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High-lift distributed teletype control system

A control system and distributed technology, applied in the control start method, aircraft power transmission, aircraft transmission, etc., can solve the problem of late start of research work, and achieve the effect of improving system safety and reducing system weight

Active Publication Date: 2020-01-10
XIAN FLIGHT SELF CONTROL INST OF AVIC
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AI Technical Summary

Problems solved by technology

[0004]At present, there is a lack of technical reserves in China for the design and effective implementation of the high-lift control system architecture of high-safety civil aircraft that meets the airworthiness standards of civil aircraft, and the research work started late. Compared with foreign advanced levels, there is a big gap in system design and equipment development, and a breakthrough in this technology is needed

Method used

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  • High-lift distributed teletype control system

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Embodiment Construction

[0025] A kind of civil aircraft high-lift distributed fly-by-wire control system provided by the application adopts a distributed structure design of function separation: high-lift control computer (HLCC) and flap motor control unit (FMCU), slat motor control unit ( SMCU) is separated and cross-linked through the internal bus of the system, adopting the configuration of "closed-loop telex normal / degraded working mode" + "open-loop electronically controlled standby working mode". The internal bus of the high-lift distributed fly-by-wire control system adopts the same time-triggered protocol bus as the internal bus of the flight control system, which facilitates the integration of the system with the fly-by-wire main flight control system and the automatic flight control system.

[0026] The high-lift distributed fly-by-wire control system includes:

[0027] Flap with position indication, slat control handle (1), backup switch (2), first high-lift control computer (3), second hi...

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Abstract

The embodiment of the invention provides a high-lift distributed teletype control system. The system comprises a control handle 1, a first high-lift control computer (HLCC) 3, a second high-lift control computer (HLCC) 4, a first flap motor control unit (FMCU) 6, a first slat motor control unit (SMCU) 5, a second flap motor control unit (FMCU) 7, a second slat motor control unit (SMCU) 8 and a mechanical transmission subsystem 9, wherein the first high-lift control computer (HLCC) 3 and the second high-lift control computer (HLCC) 4 are connected to the flap motor control unit (FMCU) 6, the first slat motor control unit (SMCU) 5, the second flap motor control unit (FMCU) 7 and the second slat motor control unit (SMCU) 8 in a bus mode and are both connected to the control handle 1, and thefirst flap motor control unit (FMCU) 6, the first slat motor control unit (SMCU) 5, the second flap motor control unit (FMCU) 7 and the second slat motor control unit (SMCU) 8 are connected to the mechanical transmission subsystem 9.

Description

technical field [0001] The invention belongs to the technical field of high-lift fly-by-wire control, and in particular relates to a structure of a civil aircraft high-lift distributed fly-by-wire control system. Background technique [0002] The civil aircraft high-lift control system is one of the key subsystems of the civil aircraft flight control system, including all the control, transmission and actuation components used to operate the aircraft's leading-edge slats and trailing-edge flaps and other high-lift devices. [0003] The high-lift control system of civil aircraft adopts distributed fly-by-wire control to reduce the weight of the system, relax the condition of power / control channel separation, optimize the system performance, improve the automatic function expansion of flap control and the high-lift control system and fly-by-wire main flight The flexibility of the comprehensive integrated design of the control system reduces the sensitivity of the aircraft to f...

Claims

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Application Information

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IPC IPC(8): B64C13/04B64C13/24B64C13/50
CPCB64C13/04B64C13/24B64C13/50Y02T50/40
Inventor 焦林冠王涛付亮刘正圆罗健晖薛劭哲
Owner XIAN FLIGHT SELF CONTROL INST OF AVIC
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